On the control of the inertial platform for a satellite launch vehicle having large attitude angles

In the case when a satellite launch vehicle is required to perform both large pitch and yaw angles in the coasting flight phase, one can utilize the programmed pitch around the outer gimbal axis of the platform and torquing the inner gimbal gyro simultaneously to realize it. In this case, it is not necessary to use the complicated four gimbal platform to fulfil the flight mission. The relationships between the vehicle´s attitude angles are discussed in detail. The design scheme for implementation of stable-element precession is also presented